The invention relates to the technical field of
aviation aircraft parts, in particular to a
titanium alloy shell part forming method which comprises the following steps: S1, primary heating and heat preservation; s2, primary upsetting is carried out; s3,
lubrication is conducted; s4, secondary heating and heat preservation; s5, secondary upsetting is conducted, specifically, backward
extrusion and
punching are conducted before secondary upsetting; according to the method, the backward
extrusion technology is carried out before secondary upsetting, the size of the obtained
forge piece is smaller than the
diameter of an existing backward
extrusion forge piece, the height of the obtained
forge piece is larger than that of the existing backward extrusion forge piece, the shape and size precision of the forge piece is improved,
metal materials are saved, and the mechanical performance of the parts is improved due to the fact that
metal fiber streamlines are profiling. The device has the characteristics of high efficiency, high quality and low
energy consumption, and has very high use value in technology and economy.